Numerical Simulation of the Flow Around Missiles dur-ing Transonic and Supersonic Flights

The article deals with the problems of reliable determination of aerodynamic characteristics of missiles and their individual elements under the conditions of transonic and supersonic flight regimes. An algorithm for numerical simulation of the aerodynamic flight characteristics of an isolated object is proposed. An algorithm for solving the problem of obtaining the aerodynamic characteristics of the whole body, as well as its individual elements, is described. A mathematical model of the flow around a solid body by transonic and supersonic turbulent flow is presented. Operating principles of the numerical scheme, methods of spatial and temporal discretization of equations, features of the boundary conditions and initial approximation are described. The studies of aerodynamic characteristics of the elements of an isolated object are performed on unstructured computational meshes. The hinge moments occurring on the deflected element of one of the opening rudders are calculated for Mach numbers 0.8 and 1.2, and the angles of attack in the range of –4 to 24 degrees. The obtained aerodynamic characteristics are compared with the experimental data of TsAGI. A conclusion about the correctness of the proposed method for studying aerodynamic characteristics of missiles in transonic and supersonic flight regimes is made.

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